Would you be able to clarify if my equations are correct?
I determine the strength of the vortex sheet using the thin airfoil theory equation:
γ = 2U∞ * (A0((1 + cos(θ)) / sin(θ)) + ƩAnsin(nθ))
To find my induced velocity for each vortex, I use the equation:
W(z) = γ / (2πr) <----...
Thanks for responding!
I've read up on the panel method code and would probably do a complete turn around on my code if not for the time constraints. I'll probably go ahead and do it later on.
If I wanted to find the induced velocity at the top and bottom surfaces due to the vortex sheet on...
First post here on pf!
I wanted to ask if it's feasible to determine velocities at the top / bottom surface of an airfoil due to the vortex sheet placed on the camber line (due to thin airfoil theory).
I'm attempting to do this because the big picture is to determine the Cp distribution...